# TCDS A9EA: De Havilland Aircraft of Canada Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: De Havilland Aircraft of Canada Limited
- Revision: 22
- Revised: February 21, 2025
- Product: Aircraft, Small Airplane
- Certification basis: CAR 3
- Registered aircraft: 92, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/02/0e/020e90a7909a74e80f5ca221f18ae49fdfd6cf8e67ec0dc742a6bebe210f2be3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID134911967820250222014510.0001
- Page: https://openairdocs.org/tcds/A9EA

## Models (5)

As the data sheet lists them.

- DHC-6-1
- DHC-6-100
- DHC-6-200
- DHC-6-300
- DHC-6-400

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
 
 
TYPE CERTIFICATE DATA SHEET NO. A9EA 
This data sheet which is a part of type certificate No. A9EA prescribes conditions and limitations under which the product for 
which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
Type Certificate Holder De Havilland Aircraft of Canada Limited  
 4100 Westwinds Drive NE 
Calgary, Alberta  
Canada T3J 4L2 
Type Certificate Holder Record Viking Air Limited 
1959 de Havilland Way 
Sidney, British Columbia 
Canada V8L 5V5 
 Bombardier Inc. 
Regional Aircraft 
123 Garratt Boulevard 
Downsview, Ontario, Canada M3K 1Y5 
de Havilland, Inc. 
123 Garratt Boulevard 
Downsview, Ontario, Canada M3K 1Y5 
I  - Model DHC-6-1 (Prototype and four Pre-Production A/C) (Normal Category), 
Approved June 22, 1966 by the FAA and April 7, 1966 by the Canadian Department of Transport (DOT) 
Engines 2 United Aircraft of Canada, Limited PT6A-20 
Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification 
CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 
hours use in any one overhaul cycle.) 
Oil Synthetic types conforming to CPWA 202, latest issue, 
(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) 
Engine rating RATING E.S.H.P. S.H.P. 
Take-off (5 min.)  *579  *550 
Max. continuous *579 *550 
*Available to 70°F (21°C) Ambient Temperature 
Engine limits Temperature Limits (Inter-Turbine) Take- 
off 1380° F (750° C) 
Max. Continuous 1380°F (750° C) 
Starting (2 sec.) 1994°F (1090° C) 
Torque Limits 
Take-off 42.5 p.s.i. (1315 ft. lb.) 
Max. Continuous 42.5 p.s.i. (1315 ft. lb.) 
Gas Generator 
Take-off 38,100 r.p.m. (101.5%) 
Max. Continuous  38,100 r.p.m. (101.5%) 
 
 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 
Rev. No. 22 - 15 8 - 8 15 8 - 15 15 - 15 15 21 21 21 21 20 21 
A9EA 
Revision No.22  
De Havilland Aircraft of Canada  
(Twin Otter) 
DHC-6-1 
DHC-6-100 
DHC-6-200 
DHC-6-300 
DHC-6-400 
February 21, 2025

Page 2 A9EA 
 
Oil Temperature 
Starting -40°C Min. 
Take-off 10°C to 99°C 
Max. Continuous 10°C to 99°C 
Oil Pressure 
Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. 
Min. (below 28,000 r.p.m.) 40 p.s.i.g. 
 
Propeller Hartzell  
 Hub HC-B3TN-3, -3B, -3BY 
 Blades T10173+1, T10173E+1 
 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs) 
Pitch Settings at 30" Station 
Feather +87° 
Take-off Low Pitch  +17° 
Idle Blade Angle +12° 
Reverse Blade Angle - 9° 
Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%) 
Max. Continuous  2200 r.p.m. (100%) 
Airspeed limits Skiplane 
(CAS) L andplane & Floatplane 
M.P.H. Knots M.P.H. Knots 
Vne (Never exceed) 232.7* 202* 210.8* 183* 
Vno (Max. structural cruising) 184.3** 160** 184.3** 160** 
Vp (Maneuvering) 149.8*** 130*** 149.8*** 130*** 
Vmc (Minimum control)  73.7  64  73.7  64 
Vfe (Flaps extended) 115.2 100 115.2 100 
Vfe (Flaps extended) 97.9  85  97.9  85 
 
*    Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft. 
** Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft. 
*** Reduce Vp - Vno above 20000 ft. 
C.G. range (Landing L andplane and Skiplane 
gear fixed) 
Forward Limit 20% M.A.C. (STA. 203.84) at all weights up to max. 
of 11000 lb. 
Aft Limit  36% M.A.C. (STA. 216.32) at all weights up to max. 
of 11000 lb. 
Floatplane 
Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. 
of 11000 lb. 
Aft Limit  32% M.A.C. (STA. 213.20) at all weights up to max. 
of 11000 lb. 
Empty weight C.G. range None 
Maximum w eights Landplane 
Take-off 11000 lb. 
Landing 11000 lb. 
Skiplane 
Take-off 11000 lb. (with Item 201(a) and (b)) 
Landing 11000 lb. (with Item 201(a) and (b)) 
Floatplane 
Take-off 11000 lb. (with Item 202(a)) 
Landing 11000 lb. (with Item 202(a)) 
Minimum Crew One (pilot). (+95.0 in.) 
No. of seats 16 (including two at Stn. +95.0 in.) - Limited by approved seating 
arrangement. (See Weight and Balance Handbook). 
Max. 17 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. 
(Approval of seating arrangement is required). 
Cargo loading conditions See Weight and Balance Handbook PSM 1-6-8 
 
0°   to   20° 
20°   to   40°

Page 3 A9EA 
 
Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.) 
500 lb. max. in rear compartment (arm +354.0 in.) 
See Weight and Balance Handbook. 
 
Fuel capacity *USABLE FUEL U.S. GALS. IMPERIAL GALS. 
 Forward Tank (+162.5 in.) 176 147 
 Rear Tank (+240.0 in.) 182 152 
 TOTAL 358 299 
*See NOTE 1(b) for Weight and Balance. 
Oil capacity * USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB. 
Port (+177.0 in.)  1.5  1.2  11 
* Se e NOTE 1(c) for Weight and Balance. 
Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for 
Altitude all occupants). 
Control surface movements Aileron (with flaps up) Up 17.5° Down 16° 
(with flaps in landing position) Up 25° Down 17.5° 
Trim Tab - or + 15° 
Geared Tab (flap up)  Up 16° Down 17.5° 
Flaps (inboard forward) 0° to 40° 
(inboard trailing) 0° to 62.5° 
(outboard forward) 0° to 26° 
(outboard trailing)  (aileron) 
Elevator Up 25° Down 16° 
Tab  Up 20° Down 25° 
Flap interconnect (flap up) Down 12° 
(flap landing) Up 12° 
Rudder Left 20° Right 21° 
Geared Tab  - or + 11° 
Trim Tab - or + 25° 
See Maintenance Manual PSM-1-6-2 for procedure to rig control 
surface movements from stop to stop. 
Serial Nos. eligible 1 to 5 inclusive. The Canadian Department of Transport Certificate of Airworthiness 
for export endorsed as noted under "Import Eligibility" must be submitted for each 
individual aircraft for which application for certification is made. 
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian 
Department of Transport "Certificate of Airworthiness for Export" signed by or for the 
Minister of Transport. This form must contain the following statement: "This certifies 
that the aircraft described below has been manufactured in conformity with data 
forming the basis for D.O.T. Type Approval No. A-82, Issue 2, dated July 29, 1966. 
(FAA Type Certificate No. A9EA)." 
Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special 
Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type 
Certificate No. A9EA issued June 22, 1966. Not approved for use in operations under 
FAR Part 135 after May 31, 1972, when FAR 135.144 becomes mandatory. (See NOTE 
3). Date of application for Type Certificate April 2, 1964. 
Equipment The  basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification and is given in 
Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the 
following item of equipment is required: 
(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-61-1A. 
Starboard (+177.0 in.) 1.5 1.2 11 
TOTAL 3.0 2.4 22

Page 4 A9EA 
 
II  - Model DHC-6-100 (Normal Category), Approved August 1, 1966 by the FAA and July 29, 1966 by the 
Canadian Department of Transport (DOT). (First Production Series) 
Engines 2 United Aircraft of Canada, Limited PT6A-20 
Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification 
CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 
hours use in any one overhaul cycle.) 
Oil Synthetic types conforming to CPWA 202, latest issue, 
(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) 
 
Engine rating RATING E.S.H.P. S.H.P. 
 Take-off (5 min.) *579 *550 
 Max. continuous *579 *550 
*Available to 70°F (21°C) Ambient Temperature 
Engine limits Temperature Limits (Inter-Turbine) 
Take-off 1380°F ( 750°C) 
Max. Continuous 1380°F ( 750°C) 
Starting (2 sec.) 1994°F (1090°C) 
Torque Limits 
Take-off 42.5 p.s.i. (1315 ft.-lb.) 
Max. Continuous 42.5 p.s.i. (1315 ft.-lb.) 
Gas Generator 
Take-off 38,100 r.p.m. (101.5%) 
Max. Continuous 38,100 r.p.m. (101.5%) 
Oil Temperature 
Starting -40°C Min. 
Take-off 10°C to 99°C 
Max. Continuous 10°C to 99°C 
Oil Pressure 
Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. 
Min. (below 28,000 r.p.m.) 40 p.s.i.g. 
Propeller Hartzell 
Hub HC-B3TN-3, -3B, -3BY 
Blades T10173+1, T10173E+1 
Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs) 
Pitch Settings at 30" Station 
Feather +87° 
Take-off Low Pitch +16° 
Idle Blade Angle +12° 
Reverse Blade Angle  -14° 
Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%) 
Max. Continuous  2200 r.p.m. (100%) 
Airspeed limits Skiplane 
(CAS) Landplane & Floatplane 
M.P.H. Knots M.P.H. Knots 
Vne (Never exceed) 232.7* 202* 210.8* 183*  
Vno (Max. structural cruising) 184.3** 160** 184.3** 160**  
Vp (Maneuvering) 149.8*** 130*** 149.8*** 130*** 
Vmc (Minimum control)  73.7  64  73.7  64 
Vfe(Flaps extended) 115.2 100 115.2 100 
0° to 20° 
Vfe (Flaps extended) 97.9 85 97.9 85 
20° to 40° 
*Reduce Vne 4.6 mph (4K) per 1000 ft. above 10000 ft. 
**Reduce Vno 3.5 mph (3K) per 1000 ft. above 10000 ft. 
***Reduce Vp - Vno above 20000 ft.

Page 5 A9EA 
 
Max Landing WT Above -20°F 
C.G. range (Landing Without Mod. 6/1020 - Same as Model 1 
gear fixed) With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" 
 
LANDPLANE 
 
11,579 
11,400 
11,000 
Max Take-Off Weight 
 
 
Max Landing WT Above -20°F 
Max Landing WT Below -20°F 
10,000 
 
9,000 20 
ARM 
203.84 
 
 
 
22 
ARM 
205.40 
 
 
 
36 
ARM 
216.32 
HORIZONTAL C.G. L IMIT - % MAC 
SKIPLANE 
11,579 
11,400 
11,000 
 
10,000 
Max Take-Off Weight 
 
 
 
9,000  
20 
ARM 
203.84 
 
22 23 
ARM 
206.18 
 
36 
ARM 
216.32 
FLOATPLANE 
Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. 
of 11,600 lb. 
Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. 
of 11,600 lb. 
Empty weight C.G. range None 
Maximum weights With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" 
Landplane (lb.)  Skipl ane (lb.)  Floatplane (lb.) 
(With Item 201(a)&(b)) (With Item 202(a)&(b)) 
Take-off 11579 11579 11600 
Landing 11400* 11400* 11600 
*See NOTE 5 - Temperature Limitations 
Without Mod. 6/1020 - Same as Model 1. 
Minimum Crew One (pilot). (+95.0 in.) 
No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating 
arrangement. (See Weight and Balance Handbook). 
Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. 
(Approval of seating arrangement is required). 
Max Landing WT Below -20°F 
GROSS WEIGHT - LB. GROSS WEIGHT - LB.

Page 6 A9EA 
 
Cargo loading limitations See Weight and Balance Handbook PSM 1-6-8 
Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.) 
500 lb. max. in rear compartment (arm +354.0 in.) 
See Weight and Balance Handbook. 
Fuel c apacity  *USABLE FUEL U.S. GAL.   IMPERIAL GAL. 
 
Forward Tank (+162.5 in.) 181 151 
Rear Tank (+240.0 in.) 197 164 
TOTAL 378 315 
*See NOTE 1(b) for Weight and Balance. 
Oil capacity * *USABLE OIL U.S. GAL. IMPERIAL GAL. WEIGHT LB. 
Port (+177.0 in.)  1.5  11.2 11 
** See N OTE  1(c) for Weight and Balance. 
Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for 
Altitude all occupants). 
Control surface movements Aileron (with flaps up) Up 17.5° Down 16° 
(with flaps in landing position) Up 25° Down 17.5° 
Trim Tab - or + 15° 
Geared Tab (flap up) Up 16° Down 17.5° 
Flaps (inboard forward)  0° to 40° 
(inboard trailing) 0° to 62.5° 
(outboard forward) 0° to 26° 
(outboard trailing) (aileron) 
Elevator Up 25° Down 16° 
Tab Up 20° Down 25° 
Flap interconnect (flap up) Down 12° 
(flap landing)  Up  12° 
Rudder  Left 20° Right 21° * 
Geared Tab - or + 11° 
Trim Tab - or + 25° 
See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface 
movements from stop to stop. 
*When Item 202(b) is incorporated then the rudder travel limits 
are: Left 17° Right 21°. 
Serial Nos. eligible 6 to 115 inclusive. The Canadian Department of Transport Certificate of Airworthiness 
for export endorsed as noted under "Import Eligibility" must be submitted for each 
individual aircraft for which application for certification is made. 
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian 
Department of Transport "Certificate of Airworthiness for Export" signed by 
or for the Minister of Transport. This form must contain the following 
statement: "This certifies that the aircraft described below has been 
manufactured in conformity with data forming the basis for D.O.T. Type 
Approval No. A-82, Issue 3, dated June 12, 1967. (FAA Type Certificate No. A9EA)." 
Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special 
Conditions for Mu lti-Engine Turbine Powered Aircraft dated November 6, 1964. Type 
Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate 
April 2, 1964. 
For this Model airplane intended for use in operations under FAR Part 135, the 
additional airworthiness requirements of Special Federal Aviation Regulation (SFAR) 
23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, 
are also included. See NOTES 3 and 8. 
Starboard (+177.0 in.) 1.5 1.2 11 
TOTAL 3.0 2.4 22

Page 7 A9EA 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification and is given in 
Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the 
following item of equipment is required: 
(a) Canadian D.O.T. approved Airplane Flight Manual, Part No. 
PSM-1-61-1A. 
 
III-   Model DHC-6-200 (Normal Category), Approved April 1, 1968 by the FAA and March 29, 1968 by the 
Canadian Department of Transport (DOT). 
This Series may be identified by: 
(1) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod. 6/1077 - Extended Nose that 
Increases the Volume and Weight Capacity of the Forward Baggage Compartment; and, 
(2) VAL (or BI) Mod. 6/1075 (Retrofit) or 6/1076 (New Production) -Increase in the Volume of the Rear 
Baggage Compartment. 
Engines 2 United Aircraft of Canada, Limited PT6A-20 
Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification 
CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 
hours use in any one overhaul cycle.) 
Oil Synthetic types conforming to CPWA 202, latest issue, 
(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) 
Engine rating RATING E.S.H.P. S.H.P. 
Take-off (5 min.)   *579 *550 
Max. continuous   *579  *550 
*Available to 70°F (21°C) Ambient Temperature 
Engine limits Temperature Limits (Inter-Turbine) 
Take-off 1380° F ( 750° C) 
Max. Continuous  1380°F  ( 750° C) 
Starting (2 sec.) 1994°F (1090° C) 
Torque Limits 
Take-off 42.5 p.s.i. (1315 ft.-lb.) 
Max. Continuous  42.5 p.s.i.  (1315 ft.- lb.) 
Gas Generator 
Take-off 38,100 r.p.m. (101.5%) 
Max. Continuous  38,100 r.p.m. (101.5%) 
Oil Temperature 
Starting -40°C Min. 
Take-off 10°C to 99°C 
Max. Continuous 10°C to 99°C 
Oil Pressure 
Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. 
Min. (below 28,000 r.p.m.) 40 p.s.i.g. 
Propeller Hartzell 
Hub HC-B3TN-3, -3B, -3BY 
Blades  T10173+1, T10173E+1 
Diameter 8 ft. 6 in. nominal 
(8 ft. 4 in. after repairs) 
Pitch Settings at 30" Station 
Feather +87° 
Take-off Low Pitch  +16° 
Idle Blade Angle  +12° 
Reverse Blade Angle  - 14°

Page 8 A9EA 
 
 
Propeller limits Propeller (Np) - Take-off 
Max. Continuous 
2200 r.p.m. (100%) 
2200 r.p.m. (100%) 
 
 
Landplane Skiplane Floatplane 
Airspeed Limits (CAS) Knots M.P.H. Knots M.P.H. Knots M.P.H. 
Vne (never exceed) 202* 232.7* 183* 211* 183* 211* 
Vno (max. structural cruising) 160** 184.3** 160** 184.3** 160** 184.3** 
Vp (design maneuvering) 130*** 149.8*** 130*** 149.8*** 130*** 149.8*** 
Vmc (minimum control) 68 78.3 68 78.3 64 78.3 
Vfe (flaps extended) 100 115.2 100 115.2 100 115.2 
0° to 20° 
Vfe (flaps extended) 85 97.9 85 97.9 85 97.9 
20° to 40°       
*Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft. 
**Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft. 
***Reduce Vp - Vno above 20000 ft. 
C.G. range (Landing With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" 
gear fixed) (All Model DHC-6-200 Aircraft Serial Nos. 116 to 230 inclusive have this 
Mod. embodied). 
 
11,579 
11,400 
 
 
11,000 
 
 
 
10,000 
 
 
9000 
20 22 36 
ARM ARM 
203.84 205.40 
HORIZONTAL C.G. LIMIT - % MAC 
ARM 
216.32 
 
11,579 
11,400 
11,000 
 
 
10,000 
 
 
 
9000 
20 22  23 36 
ARM ARM 
203.84 205.40 
206.18 
ARM 
216.32 
HORIZONTAL C.G. LIMIT - % MAC 
 
Floatplane Forward Limit 25% M.A.C. (STA. 207.74) at all 
weights up to max. of 11,600 lb. 
Aft Limit 32% M.A.C. (STA. 213.20) at all 
weights up to max. OF 11,600 lb. 
Max Take-Off Weight 
SKIPLANE 
Max Landing WT Below -20°F 
Max Landing WT Above -20°F 
GROSS WEIGHT - LB. GROSS WEIGHT - LB. 
Max Take-Off Weight 
 
Max Landing WT Above -20°F 
Max Landing WT Below -20°F 
 
LANDPLANE

Page 9 A9EA 
 
Empty weight C.G. range None 
Landplane (lb.)  Skiplane (lb.)  Floatplane (lb.) 
(With Item 201(a)&(b)) (With Item 202(a)&(b)) 
Take-off 11579 11579 11600 
Landing 11400* 11400* 11600 
*See NOTE 5 - Temperature Limitations 
Minimum Crew One (pilot). (+95.0 in.) 
No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating 
arrangement. (See Weight and Balance Handbook). 
Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. 
(Approval of seating arrangement is required). 
Cargo loading limitations See Weight and Balance Handbook (PSM 1-6-8) 
Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max. 
Forward - Long Nose 
(Mod. 6/1077) 
Rear 
Rear Extension 
( +25.0 in.) 
(+354.0 in.) 
(+391.0 in.) 
300 lb. Max. 
500 lb. Max.* 
50 lb. Max.* 
*Total Rear + Rear Extension not to exceed 500 lb. maximum. 
Fuel capacity *USABLE F UEL U.S. GALS. IMPERIAL GALS. 
 Forward Tank (+162.5 in.) 181 151 
 Rear Tank (+240.0 in.) 197 164 
 TOTAL 378 315 
*See NOTE 1(b) for Weight and Balance. 
Oil capacity  **USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB. 
Port (+177.0 in.)  1.5  1.2  11 
** See N OTE  1(c) for Weight and Balance. 
Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for 
Altitude all occupants). 
Control surface movements Aileron (with flaps up) Up 17.5° Down 16° 
(with flaps in landing position) Up 25° Down 17.5° 
Trim Tab + or -15° 
Geared Tab (flap up) Up 16° Down 17.5° 
Flaps (inboard forward) 0° to 40° 
(inboard trailing) 0° to 62.5° 
(outboard forward)  0° to 26° 
(outboard trailing) (aileron) 
Elevator Up 25° Down 16° 
Tab Up 20° Down 25° 
Flap interconnect (flap up) Down 12° 
(flap landing) Up 12° 
Rudder Left 20° Right 21° * 
(Skiplane)  Left 18° Right 21° 
Geared Tab + or -11° 
Trim Tab + or -25° 
See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface 
movements from stop to stop. 
* When Item 202(b) is incorporated then the rudder travel limits are: 
Left 17° Right 21°. 
Starboard (+177.0 in.) 1.5 1.2 11 
TOTAL 3.0 2.4 22

Page 10 A9EA 
 
Serial Nos. eligible 116 to 230 inclusive (except 130 and 210) plus any other Series aircraft that has been 
modified to embody the following significant Model 
Mod. 6/1020, 1075 or 1076, 1077. 
The Canadian Department of Transport Certificate of Airworthiness for export endorsed 
as noted under "Import Eligibility" must be submitted for each individual aircraft for 
which application for certification is made. 
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian 
Department of Transport "Certificate of Airworthiness for Export" signed by or for the 
Minister of Transport. This form must contain the following statement: "This certifies 
that the aircraft described below has been manufactured in conformity with data 
forming the basis for D.O.T. Type Approval No. A-82, Issue 4, dated December 20, 
1968 (FAA Type Certificate No. A9EA)." 
Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special 
Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type 
Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate 
April 2, 1964. 
For this Model airplane intended for use in operations under FAR Part 135, the 
additional airworthiness requirements of Special Federal Aviation Regulation (SFAR) 
23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, 
are also included. See NOTES 3 and 8. 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification and is given in 
Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the 
following item of equipment is required: 
(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-62-1A. 
IV  - Model DHC-6-300 (Normal Category), Approved May 8, 1969 by the FAA and April 25, 1969 by the 
Canadian Department of Transport (DOT). 
This is the third production series of the Type DHC-6. This series is identified 
primarily on basis of: 
(1) PT6A-27 engine in place of -20 engine; 
(2) Increase in All-Up-Weight to the maximum allowed by CAR 3 
of 12,500 lb.: 
(3) Addition of two forward exits and deletion of roof exit; and, 
(4) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod. 
6/1077 - Extended Nose that Increases the Volume and Weight 
Capacity of the Forward Baggage Compartment. 
Engines 2 United Aircraft of Canada, Limited PT6A-27 
Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification 
CPW 46. 
(MIL-G-5572C Avgas (all grades) for emergency use only - limited to 150 hours use in 
any one overhaul cycle.) 
Oil Synthetic types conforming to CPWA 202, latest issue. 
(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) 
Engine rating RATING  E.S.H.P. S.H.P. 
Take-off  652*  620* 
Max. continuous     652*              620* 
*Available to 91°F (33°C) Ambient Temperature (S.L.)

Page 11 A9EA 
 
Engine limits Temperature Limits (Inter-Turbine) 
Take-off 1336°F ( 725° C) 
Max. Continuous  1336°F ( 725° C) 
Starting (2 sec.) 1994°F (1090° C) 
Torque Limits 
Take-off 50 p.s.i. (1536 ft.-lb.) 
Max. Continuous  50 p.s.i. (1536 ft.-lb.) 
Gas Generator 
Take-off 38,100 r.p.m. (101.5%) 
Max. Continuous 38,100 r.p.m. (101.5%) 
Oil Temperature 
Starting -40°C Minimum 
Take-off 10°C to 99°C 
Max. Continuous 10°C to 99°C 
5 Minute Limit  104°C 
Oil Pressure 
Normal (28,000 r.p.m. & above) 80 to 100 p.s.i.g. 
Min. (below 28,000 r.p.m.) 40 p.s.i.g. 
Propeller Hartzell 
Hub HC-B3TN-3D (Y)* 
Blades T10282H (B)**+0 
Diameter  8 ft. 6 in. nominal 
(8 ft. 4 in. after repairs) 
*(Y) designates Zero Thrust Latches 
**(B) designates De-icing Boots. 
Pitch Settings at 30" Station 
Feather +87° 
Take-off Low Pitch +17° 
Idle Blade Angle +11° 
Reverse Blade Angle  -15° 
Propeller limits Propeller (Np) - Take-off 2110 r.p.m. (96%) 
Max. Continuous  2110 r.p.m. (96%) 
Airspeed limits 
(CAS) 
 
 
Knots 
 
Landplane 
M.P.H. Knots 
 
Floatplane 
M.P.H. 
Vmo (Max. Operating) S/L 160 184.3 160 184.3 
5000 ft. 155 179 155 179 
10000 ft. 150 173 150 173 
15000 ft. 145 167 145 167 
20000 ft. 130 149.8 130 149.8 
25000 ft. 115 132.5 115 132.5 
Vp (Design maneuvering) 136* 156.7* 136* 156.7* 
Vmc (Minimum control)  66  76  67  76 
Vfe (Flaps extended) 
0° to 10° 102 117.5 102 117.5 
10° to 37-1/2° 95 109.5 95 109.5 
*Reduce Vp to Vmo above 18000 ft.

Page 12 A9EA 
 
Max Take-Off Weight 
Max Landing Weight 
 
LANDPLANE  
AND 
WHEEL-SKIPLANE 
C.G. range (Landing gear fixed) 
 
12,500 
12,300 
11,600 
11,000 
 
 
9,000 20 25 36 
ARM 
203.84 
ARM 
207.74 
ARM 
216.32 
HORIZONTAL C.G. LIMITS - % MAC 
Floatplane F orward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. of  
  12500 lb.  
 Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. of  
  12500 lb. 
 
Empty weight C.G. range None  
Maximum weights Landplane (lb. ) 
(With Item 201(a) or (b)) 
Floatplane (lb.) 
(With Item 202(a) 
Skiplane (lb.) 
Take-off 12500 12500 12500 
Landing 12300* 12500 12300* 
 * Main Wheel Tire Pressure 
(Below -20°F) 
38 p.s.i.g. 
34 p.s.i.g. 
 
Minimum Crew One pilot. (+95.0 in.) 
No. of seats 22 (including two at Stn. +95.0 in.) - Limited by approved seating 
arrangement. (See Weight and Balance Handbook). 
Cargo loading limitations See Weight and Balance Handbook (PSM 1-63-8) 
Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max. 
Forward - Long Nose 
(Mod. 6/1077) ( +25.0 in.) 300 lb. Max. 
Rear (+354.0 in.)500 lb. Max.* 
Rear Extension (+391.0 in.)150 lb. Max.* 
* Total Rear + Rear Extension not to exceed 500 lb. maximum. 
See Item 208(a) for approved baggage pod installation. 
Fuel capacity 
 
 
 
*See NOTE 1(b) for Weight and Balance. 
Oil capacity * USABLE OIL U.S. GAL. IMPERIAL GAL.  WEIGHT LB. 
 
Port (+177.0 in.) 1.5 1.2 11 
Starboard (+177.0 in.) 1.5 1.2 11 
TOTAL  3.0 2.4 22 
* See NOTE 1(c) for Weight and Balance. 
GROSS WEIGHT - LB. 
*USABLE FUEL  U.S. GAL. IMPERIAL GAL. 
Forward Tank (+162.5 in.) 181 151 
Rear Tank (+240.0 in.) 197 164 
TOTAL  378 315

Page 13 A9EA 
 
Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for 
Altitude all occupants). 
Control surface movements Aileron (with flaps up) Up 17.5° Down 16° 
(with flaps in landing position) Up 25° Down 17.5° 
Trim Tab + or -15° 
Geared Tab (flap up) 
Flaps (inboard forward) 
(inboard trailing) 
(outboard forward) 
(outboard trailing) 
Elevator 
Up 16° 
0° to 40° 
0° to 62.5° 
0° to 26° 
(aileron) 
Up 25° 
Down 17.5° 
 
 
 
Down 16° 
Tab 
Flap interconnect (flap up) 
(flap landing) 
Up 20° 
Up 12° 
Down 25° 
Down 12° 
Rudder Left 17° Right 21° 
Geared Tab 
Trim Tab 
Left -5.5° 
+ or -25° 
Right +10° 
See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface 
movements from stop to stop. 
Serial Nos. eligible 130, 210, 231 thru 844. 
The Canadian Department of Transport Certificate of Airworthiness for export endorsed 
as noted under "Import Eligibility" must be submitted for each individual aircraft for 
which application for certification is made. 
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian 
Department of Transport "Certificate of Airworthiness for Export" signed by or for the 
Minister of Transport. This form must contain the following statement: "This certifies 
that the aircraft described below has been manufactured in conformity with data 
forming the basis for D.O.T. Type Approval No. A-82, Issue 5, dated September 10, 
1969. (FAA Type Certificate No. A9EA)." 
Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special 
Conditions for Multi-Engine Turbine Powered Aircraft dated 
November 6, 1964. 
Type Certificate No. A9EA issued June 22, 1966. 
Date of Application for Type Certificate April 2, 1964. 
For this Model airplane intended for use in operations under FAR Part 135, the 
additional airworthiness requirements of Special Federal Aviation Regulation (SFAR) 
23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, 
are also included. See NOTES 3 and 8. 
For this Model airplane intended for operations in accordance with the performance 
limitations of 14 CFR § 121.189 through 121.197, and Airplane Flight Manual 
Supplement #37 – Supplemental Performance Data, document PSM 1-63-1A, the 
following commuter category performance requirements of 14 CFR Part 23 are 
included: 
14 CFR §§ 23.45, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.65, 23.67, 23.75, 23.77, 
23.1581, 23.1583, 23.1585, 23.1587 and 23.1589 up to and including Amendment 23- 
57. See NOTES 3 and 9. 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification and is given in 
Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the 
following item of equipment is required: 
(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-63-1A. 
V  - Model DHC-6-400 (Normal Category), Approved June 11, 2012 by the FAA and June 24, 2010 by 
Transport Canada Civil Aviation (TCCA). 
This is the fourth production series of the Type DHC-6. This series is identified 
primarily on the basis of: 
(1) PT6A-34 engine in place of -27 engine; 
(2) Fully integrated Electronic Flight Instrument System (EFIS) in place of 
legacy instruments;

Page 14 A9EA 
 
(3) Upgraded electrical system; and, 
(4) Cabin safety compliance with later design standards, see “Certification basis”. 
Engines 2 Pratt & Whitney Canada Inc. PT6A-34 
Fuel For list of approved jet fuels refer to Pratt & Whitney Canada Inc. Service Bulletin No. 
1244, latest issue. 
(MIL-G-5572C Avgas (all grades) for emergency use only - limited to 150 hours use in 
any one overhaul cycle.) 
Oil  For list of approved lubricating oils refer to Pratt & Whitney Canada Inc. Service 
Bulletin No. 1001, latest issue. 
Engine rating RATING E.S.H.P. S.H.P. 
Take-off 652* 620* 
Max. continuous 652* 620* 
*Available to 108°F (42°C) Ambient Temperature (S.L.) 
Engine limits Temperature Limits (Inter-Turbine) 
Take-off 1454°F ( 790° C) 
Max. Continuous 1454°F ( 790° C) 
Starting (2 sec.)  1994°F (1090° C) 
Torque Limits 
Take-off 50 p.s.i. (1536 ft.-lb.) 
Max. Continuous 50 p.s.i. (1536 ft.-lb.) 
Gas Generator 
Take-off 38,100 r.p.m. (101.5%) 
Max. Continuous 38,100 r.p.m. (101.5%) 
Oil Temperature 
Starting -40ºF (-40°C) Minimum 
Take-off 50ºF to 210.2ºF (10°C to 99°C) 
Max. Continuous 50ºF to 210.2ºF (10°C to 99°C) 
Oil Pressure 
Normal (27,000 r.p.m. & above) 85 to 105 p.s.i.g. 
Min. (below 27,000 r.p.m.) 40 p.s.i.g. 
Propeller Hartzell 
Hub HC-B3TN-3D (Y)* 
Blades T10282H (B)**+0, T10282 (B)**+0 
Diameter  8 ft. 6 in. nominal 
(8 ft. 4 in. after repairs) 
*(Y) designates Zero Thrust Latches 
**(B) designates De-icing Boots. 
Pitch Settings at 30" Station 
Feather +87° 
Take-off Low Pitch +17° 
Idle Blade Angle +11° 
Reverse Blade Angle  -15° 
Propeller limits Propeller (Np) - Take-off 2110 r.p.m. (96%) 
Max. Continuous  2110 r.p.m. (96%)

Page 15 A9EA 
 
Max Take-Off Weight 
Max Landing Weight 
 
LANDPLANE  
AND 
WHEEL-SKIPLANE 
 
Airspeed limits 
(CAS)  Landpl ane 
Knots M.P.H. 
 
 
 
 
 
 
 
 
 
 
C.G. range (Landing gear fixed) 
 
12,500 
12,300 
11,600 
11,000 
VA (Design maneuvering) 136* 156.7* 
VMC (Minimum control)  66  76 
Vfe (Flaps extended) 0° to 10° 105 121.1 
10° to 37° 95 109.5 
*Reduce VA to VMO above 18000 ft. 
9,000 20 25 36 
ARM 
203.84 
ARM 
207.74 
ARM 
216.32 
HORIZONTAL C.G. LIMITS - % MAC 
 
Empty weight C.G. range None 
 
Maximum weights Landplane (lb.) 
(With Item 201(a) or (b)) 
Skiplane (lb.) 
Take-off 
Landing 
12500 
12300* 
12500 
12300* 
 * Main Wheel Tire Pressure 38 p.s.i.g. 
(Below -20°F) 34 p.s.i.g. 
Minimum Crew One pilot. (+95.0 in.) 
No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating 
arrangement. (See Weight and Balance Handbook). 
Cargo loading limitations See Weight and Balance Handbook (PSM 1-64-8) 
Maximum baggage Forward - Long Nose 
(Mod. 6/1077) ( +25.0 in.) 300 lb. Max. 
Rear (+354.0 in.)500 lb. Max.* 
Rear Extension (+391.0 in.)150 lb. Max.* 
* Total Rear + Rear Extension not to exceed 500 lb. maximum. 
Fuel capacity 
 
 
 
*See NOTE 1(b) for Weight and Balance. 
GROSS WEIGHT - LB. 
VMO (Max. Operating) S/L 170 196 
6700 ft. 170 196 
10000 ft. 160 184.3 
15000 ft. 145 167 
20000 ft. 130 149.8 
25000 ft. 115 132.5 
 
*USABLE FUEL  U.S. GAL. IMPERIAL GAL. 
Forward Tank (+162.5 in.) 181 151 
Rear Tank (+240.0 in.) 197 164 
TOTAL  378 315

Page 16 A9EA 
 
Oil capacity *USABLE OIL U.S. GAL. IMPERIAL GAL.  WEIGHT LB. 
 
Port (+177.0 in.) 1.5 1.2 11 
Starboard (+177.0 in.) 1.5 1.2 11 
TOTAL  3.0 2.4 22 
* See NOTE 1(c) for Weight and Balance. 
Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for 
Altitude all occupants). 
Control surface movements Aileron (with flaps up) Up 17.5° Down 16° 
(with flaps in landing position) Up 25° Down 17.5° 
Trim Tab + or -15° 
Geared Tab (flap up) Up 16° Down 17.5° 
Flaps (inboard forward) 0° to 40° 
(inboard trailing) 0° to 62.5° 
(outboard forward) 0° to 26° 
(outboard trailing) (aileron) 
Elevator Up 25° Down 16° 
Tab Up 20° Down 25° 
Flap interconnect (flap up)  Down 12° 
(flap landing) Up 12° 
Rudder Left 17° Right 21° 
Geared Tab Left -5.5° Right +10° 
Trim Tab + or -25° 
See Maintenance Manual Part No. PSM-1-64-2 for procedure to rig control surface 
movements from stop to stop. 
Serial Nos. eligible 845 and subsequent. 
The Canadian Department of Transport Certificate of Airworthiness for export endorsed 
as noted under "Import Eligibility" must be submitted for each individual aircraft for 
which application for certification is made. 
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian 
Department of Transport "Certificate of Airworthiness for Export" signed by or for the 
Minister of Transport. This form must contain the following statement: "The aircraft 
covered by this certificate has been examined and found to comply with the type design 
approved under U.S. Type Certificate No. A9EA and to be in a condition for safe 
operation.” 
Certification basis 
A - Basic Aircraft Model: 
• CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special 
Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. 
• F or this  Model airplane intended for use in operations under FAR Part 135, the additional 
airworthiness requirements of Special Federal Aviation Regulation (SFAR) 23, dated 
January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, are also 
included. See NOTES 3 and 8. 
• 14 CFR §§23.783 (a), (b), (c)(1), (c)(3) and (c)(4), 23.785 (a), (b), (c), (f), (g)(2), (h), (i), 
(j), (k) and (l), 23.787(a), (b), (c), (d), and (f) and (g), 23.803, 23.807 (a), (b), (c) and (d), 
23.815 and 23.851 (a) and (b) as amended by Amdt. 23-34; 
• 14 CFR §§23.853 (a), (c), (d)(3)(i) and (ii) and 23.1359(c) as amended by Amdt. 23-49. 
 
B - For those areas of the Basic Aircraft  Model affected by the installation of the EFIS Avionics Suite. The 
Certification Basis will add the following 14 CFR Part 23 (Normal Category) requirements at Amdt. 23- 
57, which is the latest amendment in effect on the date of application for the DHC-6-400, to those listed 
above: 
• Subpart B: §§23.143 – Amdt. 23-50 (with respect to S.O.O. 6221 AFCS [Autopilot] 
installation only) 
• Subpart D: §§23.771 – Amdt. 23-14; 23.773 – Amdt. 23-45; 23.777 and 23.779 – 
Amdt. 23-51; 23.781 – Amdt. 23-33; 23.677 (S.O.O. 6221 AFCS [Autopilot] installation 
only); and 23.867 – Amdt. 23-49; 
• Subpart E: §§23.901 – Amdt. 23-53 ; 23.963 – Amdt. 23-51; 
• Subpart F: §§23.1367 and 23.1381 – Amdt. 23-0; 23.1301, 23.1327 and 23.1335 – 
Amdt. 23-20; 23.1457 and 23.1459 – Amdt. 23-35; 23.1322, 23.1331 and 23.1357– 
Amdt. 23-43; 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1326, 23.1329, 
23.1351, 23.1353, 23.1359, 23.1361, 23.1365 and 23.1431 – Amdt. 23-49; 23.1325 – 
Amdt. 23-50; 23.1337 – Amdt. 23-51; 23.1305 – Amdt. 23-52; 23.1308 – Amdt. 23-57;

Page 17 A9EA 
 
• Subpart G: §§23.1551 – Amdt. 23-0; 23.1547 – Amdt. 23-20; 23.1501 and 23.1541 – 
Amdt. 23-21; 23.1529 – Amdt. 23-26; 23.1549 and 23.1557 – Amdt. 23-45; 23.1543, 
23.1545, 23.1553, 23.1555, 23.1559, 23.1581, 23.1583, 23.1585, 23.1587, and 23.1589 – 
Amdt. 23-50. 
 
C - Equivalent Level of Safety (ELOS) findings: 
1) Circuit Protection - 14 CFR § 23.1357(b) 
2) LED Lights -14 CFR § 23.1397(c) 
3) Airspeed Indicator Flap Markings - 14 CFR§ 23.1545(b)(4) 
4) Engine Instrument Display - 14 CFR § 23.1549(b) & (c) 
 
D - Exemptions: 
Exemption No. 17589, extending Exemption No. 13042A with time-limited conditions 
granted on September 19, 2014 for engine display colors depicting normal operating 
conditions, 14 CFR § 23.1549(b). This exemption terminates on July 31, 2018, unless sooner 
superseded or rescinded. 
 
Exemption No. 17626, for autopilot low-speed awareness, SFAR 23-1, paragraph 34(b). This 
exemption terminates on October 17, 2020, unless sooner superseded or rescinded. 
 
E - Noise Standards: 
Compliance is required for 14 CFR Part 36 at the amendment levels in effect at the date of 
application for the amended TC. 
 
F - Fuel Venting and Exhaust Emissions Standards: 
Compliance is required for 14 CFR Part 34-1 thru the most current amendments in effect on 
the date that the amended TC is granted. 
 
G - Additional Requirements: 
For this Model airplane intended for operations in accordance with the performance 
limitations of 14 CFR § 121.189 through 121.197, and Airplane Flight Manual Supplement 
#37 – Supplemental Performance Data, document PSM 1-64-1A, the following commuter 
category performance requirements of 14 CFR Part 23 are included: 
14 CFR §§ 23.45, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.65, 23.67, 23.75, 23.77, 
23.1581, 23 .1583, 23.1585, 23.1587 and 23.1589 up to and including Amendment 23-57. 
See NOTES 3, 10 and 11. 
Type Certificate No. A9EA amended March 2, 2018. 
Date of Application for amendment to Type Certificate March 3, 2014. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification 
Basis) must be installed in the aircraft for certification and is given in Viking Air Limited Report A.E.R.O.C. 
6.6.G.1. In addition, the following item of equipment is required: 
(a) Transport Canada approved Airplane Flight Manual, PSM-1-64-1A. 
 
Data Pertinent to All Models 
Datum Station 0 is 109.32 inches forward of a jig point which is marked by a plate attached to 
the bulkhead between the cockpit and the cabin. 
M.A.C. 78 inches. (The L.E. is at Station 188.24). 
Leveling means The cabin floor rails provide a surface for levelling the airplane both laterally and 
longitudinally. The cabin floor level is 15 inches below water line zero. 
Equipment The list of approved equipment, including the basic required equipment as prescribed in 
the applicable airworthiness regulations (see Certification Basis) which must be 
installed in the aircraft for certification, is given in Viking Air Limited (or Bombardier) 
Report A.E.R.O.C. 6.6.G.1. 
Approved Installations Item 201 - Ski Installations 
(a) Wheel/Ski 
Model 3000 nose-wheel/ski and Model 5500 main-wheel/ski 
installed to VAL (or BI) Drawing C6-US-1000, G.A. Ski Installation. Applicable 
to Model DHC-6-1, -100, -200, -300, and -400 Aircraft. Aircraft to be operated

Page 18 A9EA 
 
in accordance with appropriate DOT Approved VAL (or BI) Flight Manual 
Supplement. 
(b) Spring Skis 
Skis installed to VAL (or BI) Installation Drawing C6-US-1001. Applicable to 
Model DHC-6-1 and -100 Aircraft. 
Item 202 - Float Installations 
(a) CAP Model 12000 Floats on Models 1, 100 and 200 Aircraft, up to 11600 lb., or 
CAP Model 12000A and 12000B Floats on Model 300 Aircraft up to 12500 lb. 
installed to VAL (or BI) Drawing C6–UF–1000 G.A. Floatplane. Ref. DOT 
Float Type Approval F-10. 
(b) CAP Models 12000, 12000A or 12000B Floats modified in accordance with 
Field Aviation Company Limited Drawing No. 84193 to provide capability of 
loading and dropping water. Water Bomber aircraft are to be operated in 
accordance with DOT Approved Flight Manual Amendment contained in Field 
Aviation Company Report No. 6035. Water Bomber equipment is to be 
maintained in accordance with Field Aviation Company Report No. 4889. The 
operation of water bomber aircraft is within the following limitations: 
(i) Model 100 and 200 Aircraft: 
CAP 12000 Floats 
Aircraft Gross Weight 11600 lb. at C.G. Limits of 25% to 32% MAC with DH 
Mod. 6/1020 embodied. 
Maximum Water Capacity in Two Floats 425 Imperial Gal. Total. 
Maximum Fuselage Cargo 500 lb. 
Rudder travel Limits are: Left 17°, Right 21°. 
(ii) Model 300 Aircraft: 
CAP 12000A or 12000B Floats 
Aircraft Gross Weight 12500 lb. at C.G. Limits of 25% to 32% MAC. 
Maximum Water Capacity in Two Floats 450 Imperial Gal. Total. 
Maximum Fuselage Cargo 500 lb. 
Rudder travel Limits are: Left 17°, Right 21°. 
Item 203 - Intermediate Flotation Gear 
(a) VAL (or BI) Intermediate Flotation Gear Installed to VAL (or BI) Drawing C6- 
U-1000. Applicable to Models DHC-6-1, -100, -200, -300 and -400 Aircraft. 
Aircraft to be operated in accordance with appropriate DOT Approved VAL (or 
BI) Flight Manual Supplement. 
Item 204 - Aircraft Ice Protection 
(a) Models DHC-6-1, -100, -200, and -300 aircraft approved for operation in icing 
when equipped with following VAL (or BI) Modifications: 
6/1043, 6/1066, 6/1089, S.O.O. 6004, S.O.O. 6005, S.O.O. 6006, S.O.O. 6009 
and either S.O.O. 6007 or 6008. 
Aircraft to be operated in accordance with appropriate DOT Approved VAL (or 
BI) Flight Manual Supplement. 
(b) Model DHC-6-400 aircraft approved for operation in icing when equipped with 
following VAL Modifications: 
6/2042, 6/2045, S.O.O. 6168 and either S.O.O. 6202 or 6237. 
Aircraft to be operated in accordance with appropriate TCCA Approved VAL 
Flight Manual Supplement. 
Item 205 – Auto-pilot Installation 
(a) Bendix M-4C Automatic Flight Control System installed to Field Aviation Co. 
Ltd. Drawing J-500 061 per STA. SA67-7 for Model DHC-6-100. Aircraft to be 
operated in accordance with the April 22, 1968 issue of the M-4C Supplement to 
the DHC-6 Flight Manual. 
(b) Model DHC-6-400 
S.O.O. 6221 AFCS (Autopilot) 
Item 206 - Interior Installation 
(a) Commuter interior installation installed to Field Aviation Co., Ltd. Report 4961 
dated September 25, 1968. 
Item 207 - Avionics Installation 
(a) Avionics equipment installed to Field Aviation Co., Ltd. Report 4962 dated 
September 26, 1968. 
(b) Avionics equipment installed in accordance with Technical Enterprise Limited 
Report TELAIR DHC-6.

Page 19 A9EA 
 
 
Item 208 - Baggage Pod Installation 
(a) For Model DHC-6-300, baggage pod installation when installed and 
operated in accordance with Field Aviation Co., Ltd. Report No. 
6093 dated 29 March 1971. 
 
NOTES 
NOTE 1. (a) The current Weight and Balance Handbook, Part Number PSM-1-6-8, for the Models DHC-6-1, DHC-6- 
100, and DHC-6-200, PSM-1-63-8 for the Model DHC-6-300, and PSM 1-64-8 for the Model DHC-6- 
400, giving the list of equipment included in the empty weight and loading instructions, must be in each 
aircraft except in the case of operators having an approved weight control system. 
(b) The following amount of unusable fuel is included in the empty weight: 
MODEL 1          ALL OTHER MODELS 
     U.S. GAL.    IMPERIAL GAL.     U.S. GAL.        IMPERIAL GAL. 
Unusable 7.25 6.0 3.5 3.0 
(c) For weight and balance purposes the total oil including system and tank is included in the empty weight 
and equals 54 lb. at +177 in. 
NOTE 2.  The following placards must be displayed in clear view of the pilot at all times: 
(a) "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN 
COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, 
MARKINGS AND MANUALS." 
(b) "NO ACROBATIC MANEUVERS (INCLUDING SPINS) ARE APPROVED." 
(c) "DAY, NIGHT, VFR." 
(d) (1) All models except Series 400: "IFR" when the aircraft is equipped in accordance with the 
requirements for the operation intended, and either - 
(i) Vacuum system warning light installed to VAL Mod. 6/1014 to alert pilots of low vacuum 
pressure to flight instruments, or 
(ii) Pressure Instrument System, VAL Mod. 6/1046, is installed, or 
(iii) Electrical Directional Gyro and Altitude Indicators in list of approved 
equipment as defined in Viking Air Limited Report A.E.R.O.C. 6.6.G.1. are 
installed. 
(2) Series 400 (all aircraft): “IFR” 
(e) "THIS AIRPLANE IS EQUIPPED FOR OPERATION IN ICING CONDITIONS" when the aircraft is 
equipped with Item 204. 
NOTE 3. For Models DHC-6-1, -100, -200, –300, and -400 airplanes, the Structural Components Service Life Limits 
recorded in the Viking Air Limited (or Bombardier) Manual PSM 1-6-11 and approved by Transport Canada 
Civil Aviation, must be complied with. 
For Model DHC-6-400 airplanes, the Avionics Airwothiness Limitations recorded in Viking Air Limited Manual 
PSM 1-6-13 and approved by Transport Canada Civil Aviation, must be complied with. 
NOTE 4. Engine fire extinguisher system for models DHC-6-1, -100, -200, -300,and -400 Series must be installed in 
accordance with Viking Air Limited drawing C6SW1100 or other Transport Canada Civil Aviation approved 
data. 
NOTE 5. T he landing weight is 11400 lb. if the airport temperature at which the landing is to be made is at or above -20°F 
(-29°C). If the airport temperature is below -20°F, then the landing weight is restricted to 11000 lb. 
NOTE 6. The Model DHC-6-200 or -300 aircraft may have either the long nose (VAL (or BI) Mod. 6/1077) or the original 
short nose (as per the Model DHC-6-100 aircraft) in any configuration with the exception of the floatplane 
version which must have a short nose. 
NOTE 7. Maximum continuous single generator load is limited to: 
(a) 200 amps (1.0 on loadmeter) in Flight conditions up to 125°F. 
(b) 200 amps (1.0 on loadmeter) in Ground conditions up to 45°F. 
(c) 160 amps (0.8 on loadmeter) in Ground conditions from 45°F to 125°F. 
NOTE 8. For Models DHC-6-100, -200 and -300 airplanes intended for use in operations under 
FAR Part 135, one of the following must be accomplished: 
(a) Modifications recorded in Viking Air Limited (or Bombardier) Report AEROC 6.1.G.11-DHC-6 
Certified Airplanes - Basic Definitions. The appropriate DOT approved VAL (or BI) Flight 
Manual Supplement is to be inserted in the Airplane Flight Manual.

Page 20 A9EA 
 
(b) Equivalent modifications to (a) above in compliance with SFAR 23 as approved by 
the Regional Chief of an Engineering and Manufacturing Branch (Aircraft 
Engineering Division in Western Region) FAA. 
(c) Modifications in compliance with Appendix A to FAR 135. 
For Model DHC-6 Series 400 airplanes: 
All aircraft delivered are compliant with SFAR 23 and Amendment 23-1 as delivered, except as noted in the 
Exemptions. 
NOTE 9.  For Model DHC-6-300 airplanes intended for operations in accordance with the performance limitations of 14 
CFR § 121.189 through 121.197, the Airplane Flight Manual Supplement #37 – Supplemental Performance 
Data, is to be inserted in the Airplane Flight Manual, document PSM 1-63-1A. 
NOTE 10. For Model DHC-6-400 airplanes intended for operations in accordance with the performance limitations of 14 
CFR § 121.189 through 121.197, the Airplane Flight Manual Supplement #37 – Supplemental Performance 
Data, is to be inserted in the Airplane Flight Manual, document PSM 1-64-1A. 
NOTE 11. For Model DHC-6-400 airplanes: 
(a) The electrical system upgrade consists of removing the AC system; replacing the starter-generator and the 
DC system wiring, connectors, lights (strobe, navigation, nose wheel position indicator, and interior) and 
door proximity switches, and installing an increased capacity battery, 12V DC outlets in the cockpit and 
an optional pulsing landing light system. 
(b) The cockpit upgrade consists of replacing the conventional primary flight instruments, engine instruments 
and crew alerting system with an integrated Honeywell Primus Apex® EFIS avionics suite; the installation 
of / provisions for comm/nav equipment, radar altimeter (second radio altimeter optional), flight director, 
autopilot (optional), flight management system (second flight management system optional), SBAS GPS 
upgrade (optional), synthetic vision system (optional), TCAS I, TCAS II (optional), ADS-B Out 
(optional), Class A TAWS, CVR, FDR, weather radar and cabin public address system; and related 
changes to the electrical system, circuit breakers and switches. 
NOTE 12. For Model DHC-6-400 airplanes: 
In support of compliance with FAR 23.1309 at Amendment 23-57 for all avionics, the DHC-6-400 is a Class IV 
aircraft as defined in FAA Advisory Circular (AC) 23.1309-lE. 
 
 
 
 
....END....
```

## ADs (70, first 50, in force first)

- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2022-11-12](https://openairdocs.org/ad/2022-11-12): Engine Controls · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Jul 13, 2022
- [AD 2022-11-09](https://openairdocs.org/ad/2022-11-09): Wing Structure · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Jul 6, 2022
- [AD 2022-10-03](https://openairdocs.org/ad/2022-10-03): Flight Control System · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Jun 23, 2022
- [AD 2022-10-07](https://openairdocs.org/ad/2022-10-07): Flight Control System · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Jun 23, 2022
- [AD 2022-07-14](https://openairdocs.org/ad/2022-07-14): Aircraft Fuel System · Viking Air DHC-6-400. Effective May 13, 2022
- [AD 2022-03-04](https://openairdocs.org/ad/2022-03-04): Time Limits · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Mar 17, 2022
- [AD 2019-10-05](https://openairdocs.org/ad/2019-10-05): Flight Controls · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Jun 20, 2019
- [AD 2018-04-02](https://openairdocs.org/ad/2018-04-02): Flight Controls · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 2 more. Effective Mar 27, 2018
- [AD 2012-26-15 R1](https://openairdocs.org/ad/2012-26-15-R1): Navigation · Agusta AW139, A318-111, A318-112 and 70 more. Effective Dec 3, 2014
- [AD 2009-04-09](https://openairdocs.org/ad/2009-04-09): Wing front spar adapter · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Mar 26, 2009
- [AD 2008-24-01](https://openairdocs.org/ad/2008-24-01): Flight control gust locks · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 30, 2008
- [AD 2008-13-11](https://openairdocs.org/ad/2008-13-11): Corrosion · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Aug 5, 2008
- [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2000-06-03](https://openairdocs.org/ad/2000-06-03): Pneumatic Deicing Boots · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective May 5, 2000
- [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 97-23-09](https://openairdocs.org/ad/97-23-09): Inspect Fuselage Side Frames for Cracks · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 22, 1997
- [AD 97-07-10 R1](https://openairdocs.org/ad/97-07-10-R1): Wing Struts · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective May 23, 1997
- [AD 96-09-11](https://openairdocs.org/ad/96-09-11): Airplane Flight Manual (AFM) - Icing · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jun 11, 1996
- [AD 95-22-07](https://openairdocs.org/ad/95-22-07): Horizontal Stabilizer Attachment Fittings · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 27, 1995
- [AD 95-21-14](https://openairdocs.org/ad/95-21-14): Tailplane Outboard Hinge Arm Assembly · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 4, 1995
- [AD 95-18-10](https://openairdocs.org/ad/95-18-10): Elevator Root Rib · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Oct 26, 1995
- [AD 95-18-11](https://openairdocs.org/ad/95-18-11): Wing Rear Spar Attachment Caps · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Oct 26, 1995
- [AD 94-14-22](https://openairdocs.org/ad/94-14-22): Elevator Control Support · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Aug 31, 1994
- [AD 94-08-10](https://openairdocs.org/ad/94-08-10): Wing Main Spar · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jun 13, 1994
- [AD 94-04-01](https://openairdocs.org/ad/94-04-01): Wing Attachment Fittings · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Mar 31, 1994
- [AD 93-10-08](https://openairdocs.org/ad/93-10-08): Controls in Overhead Control Console · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jul 16, 1993
- [AD 93-02-04](https://openairdocs.org/ad/93-02-04): Elevator Support Assembly · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Mar 19, 1993
- [AD 90-11-01](https://openairdocs.org/ad/90-11-01): Elevator Pushrod Assembly · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Nov 16, 1990
- [AD 87-04-23](https://openairdocs.org/ad/87-04-23): Wing Support Strut · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Mar 16, 1987
- [AD 87-03-12](https://openairdocs.org/ad/87-03-12): Utility Seat - Forward Legs · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Feb 13, 1987
- [AD 80-13-11 R2](https://openairdocs.org/ad/80-13-11-R2): Rod Assemblies · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Aug 10, 1983
- [AD 82-26-06](https://openairdocs.org/ad/82-26-06): Windscreen Washer/Deicing System · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 27, 1982
- [AD 81-22-03](https://openairdocs.org/ad/81-22-03): Elevator Torque Tube · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Nov 2, 1981
- [AD 69-05-01 R2](https://openairdocs.org/ad/69-05-01-R2): Control Column Sub-assembly Cracks · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jul 7, 1980
- [AD 80-13-13](https://openairdocs.org/ad/80-13-13): Struts · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jul 1, 1980
- [AD 80-03-08](https://openairdocs.org/ad/80-03-08): Flap Control Rod Tubes · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Feb 7, 1980
- [AD 79-14-01](https://openairdocs.org/ad/79-14-01): Elevator Control System · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jul 6, 1979
- [AD 78-01-05](https://openairdocs.org/ad/78-01-05): Electrical Failure · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Feb 9, 1978
- [AD 76-13-06](https://openairdocs.org/ad/76-13-06): Lightning Protection · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Jul 6, 1976
- [AD 76-07-08](https://openairdocs.org/ad/76-07-08): Water Leakage-float Models · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Apr 12, 1976
- [AD 75-26-07](https://openairdocs.org/ad/75-26-07): Electrical Fire Hazards · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Dec 17, 1975
- [AD 75-24-15](https://openairdocs.org/ad/75-24-15): AC Power · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Nov 28, 1975
- [AD 75-12-10](https://openairdocs.org/ad/75-12-10): Autopilots · M7 Aerospace 60, 95-C55, 95-C55A and 17 more. Effective Jun 11, 1975
- [AD 75-08-02](https://openairdocs.org/ad/75-08-02): Aileron Control Cable · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Apr 7, 1975
- [AD 74-22-06](https://openairdocs.org/ad/74-22-06): Horizontal Stabilizer · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Oct 23, 1974
- [AD 74-08-11](https://openairdocs.org/ad/74-08-11): Side Seat Rail Attachment · Viking Air DHC-6-1, DHC-6-100, DHC-6-200 and 1 more. Effective Apr 18, 1974

All 70: https://openairdocs.org/tcds/A9EA/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Dehavilland DHC-6-300](https://openairdocs.org/model/dehavilland-dhc-6-300): 59 aircraft (registry code 2802630)
- [Dehavilland DHC-6-200](https://openairdocs.org/model/dehavilland-dhc-6-200): 19 aircraft (registry code 2802620)
- [Dehavilland DHC-6-100](https://openairdocs.org/model/dehavilland-dhc-6-100): 6 aircraft (registry code 2802610)
- [Dehavilland Acft Of Canada DHC 6-300](https://openairdocs.org/model/dehavilland-acft-of-canada-dhc-6-300): 4 aircraft (registry code 2805155)
- [Viking Air DHC-6-400](https://openairdocs.org/model/viking-air-dhc-6-400): 4 aircraft (registry code 9502640)
- [Boeing DHC-6-300](https://openairdocs.org/model/boeing-dhc-6-300): 0 aircraft (registry code 1386001)
- [Dehavilland Acft Of Canada DHC-6-200](https://openairdocs.org/model/dehavilland-acft-of-canada-dhc-6-200): 0 aircraft (registry code 2805150)
- [Dehavilland DHC-6-1](https://openairdocs.org/model/dehavilland-dhc-6-1): 0 aircraft (registry code 2802601)
- [Viking Air DHC-6-300](https://openairdocs.org/model/viking-air-dhc-6-300): 0 aircraft (registry code 5026394)
- [Viking DHC-6-400](https://openairdocs.org/model/viking-dhc-6-400): 0 aircraft (registry code 5026494)

## STCs approved under this data sheet (298, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA1841NM](https://openairdocs.org/stc/SA1841NM): Installation of larger windows and the lowering of the seats.. Twin Otter STC Holdings, LLC
- [STC SA12430IB](https://openairdocs.org/stc/SA12430IB): Installation of the Garmin G1000 NXi Integrated Flight Deck System. Aerocorp Avionics Solutions Inc.
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA7738SW](https://openairdocs.org/stc/SA7738SW): Installation of a freon air conditioning system.. Twin Otter STC Holdings LLC
- [STC SA943EA](https://openairdocs.org/stc/SA943EA): Replacement of de Havilland wing bleed air ducting with alternate ducting.. Texas Air Services Inc.
- [STC SA03749NY](https://openairdocs.org/stc/SA03749NY): Installation of Garmin G950 Integrated Flight Deck System. Aerocorp Avionic Solutions Inc.
- [STC SA12280IB](https://openairdocs.org/stc/SA12280IB): Installation of Wing and Outboard Fore Flap Trailing Edge Assemblies. Unity Aviation Canada Ltd.
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA12101IB](https://openairdocs.org/stc/SA12101IB): Installation of Cabin Interior Upgrade. De Havilland Aircraft of Canada Limited
- [STC SA00887LA](https://openairdocs.org/stc/SA00887LA): Installation of Pitot Heater Fail Lights.. Team J.A.S
- [STC SA02306LA](https://openairdocs.org/stc/SA02306LA): Modify existing Wipaire Inc.'s STC No. SA100CH installed on Viking Air Limited DeHavilland Model-6-300 airplanes.. Team J.A.S
- [STC SA02556LA](https://openairdocs.org/stc/SA02556LA): Installation of Passenger Utility Seats. Team J.A.S
- [STC SA02649LA](https://openairdocs.org/stc/SA02649LA): Installation of Max-Viz 2300 Enhanced Vision System. Team J.A.S
- [STC SA02682LA](https://openairdocs.org/stc/SA02682LA): This STC approves the Viking Air Limited DHC-6-300 landplane to operate in the commuter category, to takeoff at a maximum weight of 14,000 pounds and land at a maximum weight of 13,800 pounds, the installation of Pratt & Whitney Canada PT6A-34 engines rated at 750 SHP, and associated modifications. Team J.A.S
- [STC SA02730LA](https://openairdocs.org/stc/SA02730LA): Installation of High-Flow 250 AMP Starter-Generators. Team J.A.S
- [STC SA02806LA](https://openairdocs.org/stc/SA02806LA): Structural Provisions for AFT Camera Hatch. Team J.A.S
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA8709SW](https://openairdocs.org/stc/SA8709SW): Installation of a Traffic Alert and Collision Avoidance System I (TCAS I) model TCAS 791/791A.. Acron Aviation Inc.
- [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica
Cellular Module (avCM. Aircraft Systems and Manufacturing Inc.
- [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [STC SA00221IB](https://openairdocs.org/stc/SA00221IB): Installation of the Nose Cone Research Provisions. Rocky Mountain Aircraft
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA00345BO](https://openairdocs.org/stc/SA00345BO): Installation of an NVIS / NVG Compatible Lighting System. ATI Engineering Services LLC
- [STC SA00196IB](https://openairdocs.org/stc/SA00196IB): Installation of the Replacement Aluminum Cargo Floor Panels. Rocky Mountain Aircraft
- [STC SA02380LA](https://openairdocs.org/stc/SA02380LA): Re-Life of the Viking Air Limited Model DHC-6 Series 100, 200 and 300 fuselage, horizontal stabilizer, and vertical stabilizer. IKHANA Group Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA00171IB](https://openairdocs.org/stc/SA00171IB): Installation of the Radar Altimeter Mounts (Structural Provisions Only). Rocky Mountain Aircraft
- [STC SA00157IB](https://openairdocs.org/stc/SA00157IB): Installation of the Cabin Audio System Upgrade. Unity Aviation Canada Ltd.
- [STC SA00152IB](https://openairdocs.org/stc/SA00152IB): Installation of High Back Seat Modification. Kenn Borek Air Ltd.
- [STC SA02457LA](https://openairdocs.org/stc/SA02457LA): Re-Life flight controls. IKHANA Group Inc.
- [STC SA3532NM](https://openairdocs.org/stc/SA3532NM): Installation of Hartzell/Raisbeck Quiet Turbofan Propeller System.  Suitable for DHC-6-300 airplanes with PT6A-27 engines.. Raisbeck Engineering Inc.
- [STC SA00129IB](https://openairdocs.org/stc/SA00129IB): Decommission of Standard Operators Options (S.O.O.) 6095 Fuel System. Kenn Borek Air Ltd.
- [STC SA00085IB](https://openairdocs.org/stc/SA00085IB): Installation of Elevator Replacement Trailing Edge. Rocky Mountain Aircraft
- [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA04482CH](https://openairdocs.org/stc/SA04482CH): INSTALL TELEDYNE FLIR INC STAR SAFIRE 380-HDc FLIR IMAGING SYSTEM WITH LASER RANGE FINDER (LRF). MAG AEROSPACE
- [STC SA04550AT](https://openairdocs.org/stc/SA04550AT): Main Wheel and Brake Assembly for the Viking Air DHC-6 Series aircraft. PMA Design and Manufacturing
- [STC SA1065GL](https://openairdocs.org/stc/SA1065GL): Install Aircraft Wheel and Brake CONVERSION Kit 199-92, N/C.. KAMAN Corporation Aircraft Wheel and Brake LLC
- [STC SA00061IB](https://openairdocs.org/stc/SA00061IB): Activation of the Garmin GTN 750 (Xi) TAWS-A. Rocky Mountain Aircraft
- [STC SA00060IB](https://openairdocs.org/stc/SA00060IB): Installation of LED Replacement Cockpit Panels. Rocky Mountain Aircraft
- [STC SA00054IB](https://openairdocs.org/stc/SA00054IB): Installation of Pitot Heat Indication System. Rocky Mountain Aircraft
- [STC SA00042IB](https://openairdocs.org/stc/SA00042IB): Installation of Engine Chip Detectors. Rocky Mountain Aircraft
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA04701NY](https://openairdocs.org/stc/SA04701NY): Replacement of Fixed Wing Control Cables. Thunder Bay Aviation Ltd

All 298: https://openairdocs.org/tcds/A9EA/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.